Methods and system for disassembling a machine

ABSTRACT

A system and methods for disassembling a rotary machine are provided. The rotary machine includes a casing having a plurality of arcuate channels. The system includes a reaction bridge that is configured to couple to the casing of the rotary machine such that the reaction bridge is moveable along a length of the casing. The reaction bridge includes a front support and a rear support that is substantially parallel to the front support. Each of the supports includes a first leg, a second leg, and a support beam extending therebetween. A force device including an actuator and an engaging rod extending therefrom is coupled to the reaction bridge. The force device is configured to apply a force substantially tangentially to a segment positioned in one of the casing arcuate channels.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a continuation and claims priority to U.S. patentapplication Ser. No. 12/110,729 filed Apr. 28, 2008 for “METHODS ANDSYSTEM FOR DISASSEMBLING A MACHINE,” which is hereby incorporated byreference herein in its entirety.

BACKGROUND OF THE INVENTION

The field of the invention relates generally to gas turbine engines, andmore particularly, to a system and methods for removing stator vanesegments from a turbine engine.

At least some known gas turbine engines include, in serial flowarrangement, a high-pressure compressor for compressing air flowingthrough the engine, a combustor wherein fuel is mixed with thecompressed air and ignited to form a high temperature gas stream, and ahigh pressure turbine. Hot combustion gases are channeled downstreamfrom the combustor towards the turbine, wherein energy is extracted fromthe combustion gases for use in powering the compressor, as well asproducing useful work to propel an aircraft in flight or to power aload, such as in an electrical generator. Some known gas turbine enginesmay also include a low-pressure compressor, or booster compressor, tosupply compressed air to the high pressure compressor.

Known compressors include a compressor casing that may include upper andlower casing sections that are coupled about a rotor assembly. Knowncompressors include a plurality of alternating rows ofcircumferentially-spaced stator and rotor blades. Each row of rotor andstator blades includes a series of airfoils that each include a pressureside and a suction side that are coupled together at leading andtrailing edges. Each stator blade airfoil extends radially inward from astator support ring that is inserted into channels that arecircumferentially formed in axial succession within a radially-innerside of the combustor casing. Each stator ring is sized and shaped toreceive a plurality of stator blade segments that extendcircumferentially in a row between a pair of adjacent rows of rotorblade assemblies.

During operation, leading and trailing edges and/or an outer tip of thestator blade may deteriorate or become damaged due to oxidation, thermalfatigue cracking, or erosion caused by abrasives and corrosives in theflowing gas stream. Over time such deterioration may cause some knownstator blades to fail, resulting in the airfoil portion becomingdetached from a dovetail portion of the blade. In some instances, bladefailures have caused catastrophic damage within their engine. Tofacilitate mitigating such operational effects, blades are periodicallyinspected for damage, to enable a determination of an amount of damageand/or deterioration to be made. Blades are generally replaced if thedamage and/or deterioration meets a certain pre-determined threshold.Alternatively, if the blades have not lost a substantial quantity ofmaterial, the blades may be repaired.

For example, at least one known method of replacing stator support ringsegments requires the removal of the upper compressor section casing androtor assemblies. Following rotor assembly removal, each stator bladesegment is heated and after reaching a desired temperature, the segmentis quenched to facilitate rapid cooling. Each segment is then withdrawnfrom its respective channel using, for example, a pneumatic peeninghammer. A newly fabricated segment is then inserted into the casingchannel. Alternatively, after being removed from the rotor assembly,each damaged or deteriorated segment is repaired and refurbished priorto being replaced within the casing channel. However, rotor assemblyremoval, reinsertion, and compressor reassembly may be a time-consumingand expensive process that may significantly increase repair time andpower generator outages.

BRIEF DESCRIPTION OF THE INVENTION

In one aspect, a method for disassembling a rotary machine is provided.The method includes at least partially disassembling a casing of therotary machine to provide access to an arcuate channel defined in thecasing. The method also includes coupling a reaction bridge to thecasing of the rotary machine. The reaction bridge includes a first leg,a second leg, and a support beam extending therebetween. The reactionbridge also includes a force device removably coupled to the reactionbridge. The method further includes engaging a segment positioned in thearcuate channel using a force device, applying a force to the segmentsuch that the segment is repositioned within a portion of the arcuatechannel, and removing the segment from the arcuate channel.

In another aspect, a system for disassembling a rotary machine isprovided. The rotary machine includes a casing including a plurality ofarcuate channels defined therein. The system includes a reaction bridgeconfigured to removably couple to the casing of the rotary machine suchthat the reaction bridge is moveable along a length of the casing. Thereaction bridge includes a front support and a rear support that issubstantially parallel to the front support. Each of the front and rearsupports include a first leg, a second leg, and a support beam extendingtherebetween. The system also includes a force device including anactuator and an engaging rod extending therefrom. The force device isremovably coupled to the reaction bridge. The force device is configuredto apply a force substantially tangentially to a segment positioned inone of the casing arcuate channels.

In yet another aspect, a method for disassembling a rotary machine isprovided. The rotary machine includes a casing having an arcuate channeldefined therein. The method includes applying an inward force to asegment positioned in the arcuate channel of the rotary machine using afirst force device that is removably coupled to a reaction bridge. Thereaction bridge is coupled to the casing of the rotary machine andincludes a first leg, a second leg, and a support beam extendingtherebetween. The inward force is applied such the segment isrepositioned within a portion of the arcuate channel. The method alsoincludes determining that the segment is mechanically frozen within thechannel, and applying an outward force to the segment using a secondforce device removably coupled to the reaction bridge such that thesegment is further repositioned within a portion of the arcuate channel.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic view of an exemplary gas turbine engine;

FIG. 2 is an enlarged cross-sectional view of a portion of a compressorthat may be used with the gas turbine engine shown in FIG. 1 and takenalong area 2;

FIG. 3 is a perspective view of an exemplary stator blade ring segmentthat may be used with the compressor shown in FIG. 2;

FIG. 4 is a top view of an exemplary drilling system.

FIG. 5 a fragmentary elevation view of the drilling system shown in FIG.4.

FIG. 6 is an end perspective view of a segment removal system coupled tothe compressor shown in FIG. 2.

FIG. 7 is a side perspective view of the segment removal system coupledto the compressor shown in FIG. 2.

FIG. 8 is an elevation view of an exemplary force device that may beused with the segment removal system shown in FIGS. 6 and 7.

FIG. 9 is a side perspective view of the force device used with thesegment removal system shown in FIGS. 6 and 7.

FIG. 10 is an elevation view of a force device used with segment removalsystem shown in FIGS. 6 and 7.

FIG. 11 is a side view of the force device shown in FIG. 10 and usedwith segment removal system shown in FIGS. 6 and 7.

FIG. 12 is an assembly view of an exemplary clevis assembly used withthe force device shown in FIGS. 10 and 11.

FIG. 13 is a partial elevation view of the exemplary clevis assemblyshown in FIG. 12.

FIG. 14 is an elevation view of a pivot cradle assembly that may be usedwith the force device shown in FIGS. 10 and 11.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 1 is a schematic illustration of an exemplary gas turbine engine100. Engine 100 includes a compressor 102 and a plurality of combustors104. Combustor 104 includes a fuel nozzle assembly 106. Engine 100 alsoincludes a turbine 108 and a common compressor/turbine rotor 110(sometimes referred to as rotor 110).

FIG. 2 is an enlarged cross-sectional view of a portion of compressor102 taken along area 2 (shown in FIG. 1). Compressor 102 includes arotor assembly 112 and a stator assembly 114 that are positioned withina casing 116 that at least partially defines a flow path 118 incooperation with at least a potion of a casing radially inner surface119. In the exemplary embodiment, rotor assembly 112 forms a portion ofrotor 110 and is rotatably coupled to a turbine rotor (not shown). Rotorassembly 112 also partially defines an inner flow path boundary 120 offlow path 118, and stator assembly 114 partially defines an outer flowpath boundary 122 of flow path 118, in cooperation with inner surface119. Alternatively, stator assembly 114 and casing 116 are formed as aunitary and/or integrated component (not shown).

Compressor 102 includes a plurality of stages 124, wherein each stage124 includes a row of circumferentially-spaced rotor blade assemblies126 and a row of stator blade assemblies 128, sometimes referred to asstator vanes. Rotor blade assemblies 126 are coupled to a rotor disk 130such that each blade assembly 126 extends radially outwardly from rotordisk 130. Moreover, each assembly 126 includes a rotor blade airfoilportion 132 that extends radially outward from a blade coupling portion134 to a rotor blade tip portion 136. Compressor stages 124 cooperatewith a motive or working air including, but not limited to, air, suchthat the motive air is compressed in succeeding stages 124.

Stator assembly 114 includes a plurality of rows of stator rings 137,sometimes referred to as segmented stators, stator-in-rings, statorsupport rings, and/or stator dovetail rings. Rings 137 are inserted intopassages or channels 139 that extend circumferentially, in axialsuccession, within at least a portion of casing 116. Each channel 139 isdefined to be substantially axially adjacent to a portion of casing 116that is radially outward from and opposite rotor blade tip portions 136.Each stator ring 137 is sized and shaped to receive a plurality ofstator blade assemblies 128 such that each row of blade assemblies 128is positioned between a pair of axially adjacent rows of rotor bladeassemblies 126. In the exemplary embodiment, each blade assembly 128includes an airfoil portion 140 that extends from a stator bladedovetail portion (not shown in FIG. 2) to a stator blade tip portion144. Compressor 102 includes one row of stator vanes 138 per stage 124,some of which are bleed stages (not shown in FIG. 2). Moreover, in theexemplary embodiment, compressor 102 is substantially symmetric about anaxial centerline 152.

In operation, compressor 102 is rotated by turbine 108 via rotor 110.Air collected from a low pressure region 148 via a first stage ofcompressor 102 is channeled by rotor blade airfoil portions 132 towardsairfoil portions 140 of stator blade assemblies 128. The air is at leastpartially compressed and a pressure of the air is at least partiallyincreased as the air is channeled through flow path 118. Morespecifically, the air continues to flow through subsequent stages thatare substantially similar to the first stage 124 with the exception thatflow path 118 narrows with successive stages to facilitate compressingand pressurizing the air as it is channeled through flow path 118. Thecompressed and pressurized air is subsequently channeled into a highpressure region 150 for use within turbine engine 100.

FIG. 3 is a perspective view of an exemplary stator blade ring segment154 that may be used with compressor 102 (shown in FIG. 2). In theexemplary embodiment, segment 154 includes a plurality of stator bladepassages 156 that are each defined within segment 154. Moreover, eachpassage 156 is sized and shaped to receive a stator blade assembly 128therein. Each assembly 128 includes a stator blade dovetail portion 158that enables stator blade assemblies 128 to be coupled to casing 116 viastator blade passages 156. In the exemplary embodiment, each statorblade ring segment 154 is coupled to casing 116 via coupling methodsthat include, but are not limited to, a friction fit, the use ofretention hardware (not shown), a welding process, and/or any othermechanical coupling means, and forming segments 154 integrally withcasing 116. A plurality of ring segments 154 are inserted into eachchannel 139 such that segments 154 extend substantiallycircumferentially within compressor casing 116 and such thatcircumferentially adjacent segments 154 abut each other. As such, ringsegments 154 form at least a portion of outer path flow boundary 122.

Referring to FIGS. 4 and 5, FIG. 4 is a top view of an exemplarycompressor 200 that includes a casing section 202 and an exemplarydrilling system 203. FIG. 5 is a fragmentary elevation view ofcompressor 200 and drilling system 203, and illustrates five statorblade stages S0, S1, S2, S3 and S4 within casing section 202. Arrow 204represents an airflow direction through compressor 200. In the exemplaryembodiment, casing section 202 includes a first horizontal flange 206and a second horizontal flange 208 that each extend radially outwardfrom a mid compressor case 209. Casing section 202 includes a pluralityof channels 210, including channel ends 211, that are circumferentiallydefined in axial succession within at least a portion of casing section202. A plurality of blade segments 212 including stator blades (notshown) are inserted into each channel 210 such that segments 212 extendsubstantially circumferentially within casing section 202 and such thatcircumferentially adjacent segments 212 abut each other. In theexemplary embodiment, each channel 210 includes three segments 212.Alternatively, each channel 210 may include any number of segments 212that enables compressor 200 to function as described herein.

In preparation for removing blade segments 212, at least one mountingplate 214 including a top surface 215, is coupled to either firsthorizontal flange 206 and/or to second horizontal flange 208. Mountingplate 214 includes a plurality of holes 216 that enable drilling system203 to be coupled securely thereto, as described in detail below. Amounting plate inner surface 218 includes a series of recessed portions220 that substantially align with channel ends 211. Mounting plate innersurface 218 is aligned with segment inner surface 221 at a matingsurface 222 and is coupled thereto. In the exemplary embodiment,mounting plate 214 is fabricated from steel. Alternatively, mountingplate 214 may be fabricated from any material that enables drillingsystem 203 to function as described herein.

In the exemplary embodiment, drilling system 203 includes at least onedrill 230, a bushing locator plate 232, a plurality of drill guidebushings 234 and a plurality of fasteners 236 extending therebetween.Bushing locator plate 232 is sized to be positioned upon mounting platetop surface 215 such that plate 232 is substantially aligned withmounting plate 214 and such that a plurality of recessed sections 238defined within plate 232 are aligned with mounting plate recessedportions 220. In the exemplary embodiment, drill 230 is magneticallycoupled to mounting plate 214. Alternatively, drill 230 may be coupledto mounting plate 214 using any means that enables drill 230 to functionas described herein. In the exemplary embodiment, drill guide bushings234 are positioned at each channel end 211, and coupled to bushinglocator plate 232 via a plurality of fasteners 236.

In operation, drilling system 203 facilitates removal of stator vanesegment 212. Specifically, in the exemplary embodiment, drill 230 formsa reference bore (not shown) in segment end 240. Bushing locator plate232, drill guide bushings 234, and fasteners 236 are then removed anddrill 230 forms three holes (shown in FIG. 12) in segment end 240 thateach extend from a predetermined depth. More specifically, in theexemplary embodiment, the three holes are bored into segment outerportion 241, through stator blade dovetail portion 242, and partiallyinto an adjacent stator blade segment portion 244.

Referring to FIGS. 6 and 7, FIGS. 6 and 7 are a respective endperspective view and a side perspective view of compressor 200 with anexemplary segment removal system 300 installed. As described herein,compressor 200 includes casing section 202 and rotor 110. In theexemplary embodiment, segment removal system 300 includes a reactionbridge 305 that includes a forward support 308 and rear support 310 thatare substantially parallel to each other. Moreover, each support 308,310 includes a first leg 312 that includes an upper end 314 and a lowerend 316, a second leg 318 that includes an upper end 320 and a lower end322, and a support beam 323 that, in the exemplary embodiment, extendsbetween upper end 314 and upper end 320. In the exemplary embodiment,reaction bridge 305 is coupled to casing section 202 via mounting plate214. More specifically, and in the exemplary embodiment, lower end 316is coupled to first horizontal flange 206 via mounting plate 214, andlower end 322 is coupled to second horizontal flange 208 via mountingplate 214, such that reaction bridge 305 extends over casing section 202and rotor 110. Moreover, in the exemplary embodiment, segment removalsystem 300 includes a pair of multi-position slides 324 that are eachcoupled to first leg upper end 314 and a pair of multi-position slides324 that are coupled to second leg upper end 320. Multi-position slides324 each include a plurality of placement holes 326, as described inmore detail herein. Alternatively, segment removal system 300 mayinclude any number of multi-position slides 324 that enables segmentremoval system 300 to function as described herein. In operation,reaction bridge 305 is movable along a length L₁ of mounting plate 214,and is coupled to mounting plate 214 using holes 216 and at least onefastening mechanism (not shown).

Referring to FIGS. 8 and 9, FIG. 8 is an elevation view of compressor200 and segment removal system 300, with an exemplary force device 400installed. FIG. 9 is a side perspective view of compressor 200 andsegment removal system 300 with force device 400 installed. In theexemplary embodiment, force device 400 includes an actuator 410 and anengaging rod 420 that extends therefrom. Rod 420 has a defined stokelength L₂. In the exemplary embodiment, actuator 410 is a 75-tonhydraulic ram and force device has a 13 inch stroke length.Alternatively, force device 400 maybe any device that enables segmentremoval system 300 to function as described herein. Force device 400 iscoupled to reaction bridge 305 via multi-position slide 324.Specifically, multi-position slide 324 is configured, via placementholes 326, to enable force device 400 to be positioned at a variouspositions along a length L₃ along multi-position slide 324 depending ona location of reaction bridge 305 relative to mounting plate 214.

In operation, and in the exemplary embodiment, actuator 410 forcesengaging rod 420 against segment outer end 240 (see FIGS. 4 and 5) tofacilitate removing segment 212 from channel 210. More specifically, inthe exemplary embodiment, engaging rod 420 induces pressuresubstantially tangentially against segment end 240 for a stroke lengthL₂. Upon achieving the maximum stroke length L2, engaging rod 420 isretracted and a mock segment 430 is inserted into segment 212 to enableforce device 400 to maintain contact with the segment end 240 beyond themaximum stroke length L2. In the exemplary embodiment, actuator 410 thenpushes engaging rod 420 to re-engage segment end 240 via mock segment430. In the exemplary embodiment, force is applied against segment end240 until segment 212 is fully removed from channel 210. Alternatively,force is applied to segment end 240 until segment 210 reaches a positionwhere it may be pulled from channel 210, as described herein.

Referring to FIGS. 10 and 11, FIG. 10 is an elevation view of compressor200 and segment removal system 300, with an exemplary force device 500installed. FIG. 11 is a side perspective view of compressor 200 andsegment removal system 300 with force device 500 installed. In theexemplary embodiment, force device 500 includes an actuator 510, aclevis assembly 512 and an engaging rod assembly 514 that extendstherebetween. In the exemplary embodiment, actuator 510 is coupled toreaction bridge 305 and multi-position slide 324 via a pivot cradleassembly 516. Actuator 510 includes an enclosed axial channel (notshown). In the exemplary embodiment, engaging rod assembly 514 includesa threaded rod 522 that includes a first end 524 and an opposite secondend 526 and is coupled to actuator such that first end 524 extendsthrough axial chamber (not shown) of actuator 510 and extends a lengthL₄ outward from actuator 510. In the exemplary embodiment, attachmentrod second end 526 is threadedly coupled to clevis assembly 512, asdescribed in detail herein. Moreover, in the exemplary embodiment,actuator 510 is a 30 ton hydraulic actuator. Alternatively, actuator 510may be any pneumatic, mechanical or electrical actuator that enablessegment removal system to function as described herein.

Referring to FIGS. 12 and 13, FIG. 12 is an exploded view of anexemplary clevis assembly 512. FIG. 13 is a partial elevation view ofexemplary casing section 202 with exemplary clevis assembly 512 coupledto segment outer end 240. In the exemplary embodiment, clevis assembly512 includes a first component 602, a second component 604 and a jointcomponent 606. First component 602 includes a first end 608 and a secondend 610 and is threadedly coupled to attachment rod second end 526 viathreaded hole 612. In the exemplary embodiment, first component secondend 610 includes a T-shaped extension 614 and mating hole 616 definedtherein.

In the exemplary embodiment, second component 604 has a substantiallyrectangular cross-sectional profile and includes a first side 630, asecond side 632, a third side 634 that is opposite first side 630.Moreover, component 604 also includes a forth side 636 that is oppositesecond side 632, and an upper portion 640 that includes an open channel642 passing from second side 632 to fourth side 636. Upper portion firstside 630 and third side 634 each include a mating hole 644 definedtherein that are aligned such that mating hole 644 extends throughchannel 642. In the exemplary embodiment, channel 642 includes a lowersurface 646 and second component 604 includes a bottom surface 648.Three bolt holes 650 extend between channel lower surface 646 and bottomsurface 648. Bolt holes 650 enable second component 604 to be coupled toblade segment 212 to facilitate removing segment 212 from statorchannels 210.

Joint component 606, in the exemplary embodiment, includes a cubicportion 660 and an extension portion 662. Cubic portion 660 includes afirst side 664, a second side 666, a third side 668 that is oppositefirst side 664, and a fourth side 670 that is opposite second side 666.Portion 660 also includes a mating hole 672 that extends from secondside 666 to fourth side 670. Cubic portion 660 includes an open channel674 that extends from first side 664 to third side 668, and that issized and oriented to receive first component extension 614 such thatfirst component mating hole 616 and cubic portion mating hole 672 arealigned and receive a first clevis pin 675 when assembled, such thatcomponents 602 and 606 are rotatable about pin 675. Extension portion662 includes a hole 676 defined therein. Second component open channel642 is sized and oriented to receive joint component extension portion662 and is oriented such that second component mating hole 644 andextension portion mating hole 676 are aligned to receive a second clevispin 678 when assembled, such that components 604 and 606 are rotatableabout pin 678. In the exemplary embodiment, first clevis pin 675 andsecond clevis pin 678 are substantially perpendicular to each other.

FIG. 14 is an elevation view of actuator 510 with pivot cradle assembly700. Reaction bridge 702 includes a forward support 704 and rear support706 that is substantially parallel to support 704. A multi-positionslide 708 is coupled to forward support 704 and to rear support 706. Atrunnion assembly 710 is coupled to a top surface 712 of eachmulti-position slide 708. Trunnion assembly 710 includes a first support720, a second support 722 and a rotatable support 724 coupledtherebetween. Rotatable support 724 includes a first side 726, a secondside 728, a third side 730 that is opposite first side 726, a fourthside 732 that is opposite second side 728, a top surface 734 and abottom surface 736. In the exemplary embodiment, a trunnion pin (notshown) extends substantially perpendicularly outward from both secondside 728 and fourth side 732. First support 720 has a hole 738 definedtherein that is sized to receive a second side trunnion pin (not shown).Similarly, second support 722 has a hole defined therein that is sizedto receive fourth side trunnion pin (not shown).

Rotatable support 724 includes a channel (not shown) defined thereinthat extends from top surface 734 to bottom surface 736 and that issized and oriented to receive threaded rod 522. Actuator 510 ispositioned against rotatable member top surface 734 such that actuatoraxial channel (not shown) and rotatable support channel (not shown) aresubstantially aligned. Threaded rod 522 is positioned within theactuator axial channel and the rotatable support channel such that alength extends L₃ from actuator 510. An encapsulating bushing assembly800 is coupled to the length L₃ of exposed rod 522.

During operation, actuator 510 exerts a pulling force to threaded rod522, that, when coupled to segment outer end 240, facilitates theremoval of segment 212 from channel 210. Encapsulating bushing assembly800 is positioned upon the length of exposed threaded rod to facilitatepreventing threaded rod 522 from disconnected from the system, shouldthread rod 522 experience a structural failure during operations. Pivotcradle assembly 700 and trunnion assembly 710 facilitate rotation ofactuator 510 during operations.

The above-described methods and system provide a cost-effective andreliable means to facilitate the disassembly of gas turbine enginecomponents. Specifically, stator vane segment removal may beaccomplished without removing the rotor assembly from the engine. Assuch, system outage duration due to repairs may be significantlyreduced. Additionally, the segment removal system described hereinfacilitates reducing segment removal time by enabling a user to quicklychange from a segment pushing device to a segment pulling device.

Exemplary embodiments of a process and system for disassembling amachine, particularly removing stator vane sections from a gas turbineengine is described above in detail. The process and system are notlimited to the specific embodiments described herein, but rather, stepsof the process and components of the system may be utilizedindependently and separately from other steps and components describedherein.

While the invention has been described in terms of various specificembodiments, those skilled in the art will recognize that the inventioncan be practiced with modification within the spirit and scope of theclaims.

What is claimed is:
 1. A method for disassembling a rotary machine, said method comprising: at least partially disassembling a casing of the rotary machine to provide access to an arcuate channel defined in the casing; coupling a reaction bridge to the casing of the rotary machine, the reaction bridge including a first leg, a second leg, and a support beam extending therebetween, the reaction bridge further including a force device removably coupled to the reaction bridge; engaging a segment positioned in the arcuate channel using the force device; applying a force to the segment such that the segment is repositioned within the arcuate channel; and removing the segment from the arcuate channel.
 2. A method in accordance with claim 1, wherein applying a force to the segment further comprises applying the force substantially tangentially to the segment.
 3. A method in accordance with claim 2, wherein applying the force substantially tangentially to the segment further comprises applying an inward force substantially tangentially to an end of the segment at a first end of the arcuate channel to reposition the segment within the arcuate channel away from the first end.
 4. A method in accordance with claim 2, wherein removing the segment from the arcuate channel further comprises pushing the segment from the arcuate channel.
 5. A method in accordance with claim 1, wherein engaging the segment further comprises coupling the force device to the segment with an adaptor, wherein the force device includes an actuator and a rod coupled to the actuator.
 6. A method in accordance with claim 5, wherein removing the segment from the arcuate channel further comprises pulling the segment from the arcuate channel.
 7. A method in accordance with claim 5, wherein coupling the force device to the segment with an adaptor further comprises: drilling a hole in an end of the segment; and threadably coupling the adaptor to the end of the segment using the hole.
 8. A system for disassembling a rotary machine that includes a casing including a plurality of arcuate channels defined therein, said system comprises: a reaction bridge configured to removably couple to the casing of the rotary machine such that said reaction bridge is moveable along a length of the casing, said reaction bridge comprising a front support and a rear support that is substantially parallel to said front support, each of said front and rear supports comprising a first leg, a second leg, and a support beam extending therebetween; and a force device comprising an actuator and an engaging rod extending therefrom, said force device removably coupled to said reaction bridge, said force device configured to apply a force substantially tangentially against a segment positioned in one of the casing arcuate channels.
 9. A system in accordance with claim 8 further comprising at least one multi-position slide coupled to said reaction bridge, said at least one multi-position slide configured to support said force device.
 10. A system in accordance with claim 9, wherein said at least one multi-position slide comprises a plurality of holes extending therethrough such that said force device is moveable along a length of said at least one multi-position slide.
 11. A system in accordance with claim 8 further comprising a mounting plate configured to couple to the casing to support said reaction bridge.
 12. A system in accordance with claim 11 further comprising a plurality of guide plates positioned on said mounting plate to facilitate reducing deterioration of the machine during disassembly.
 13. A system in accordance with claim 8, wherein said actuator is a hydraulic ram.
 14. A system in accordance with claim 13, wherein said hydraulic ram is a 75-ton hydraulic ram with a 13 inch stroke length.
 15. A method for disassembling a rotary machine that includes a casing having an arcuate channel defined therein, said method comprising: applying an inward force to a segment positioned in the arcuate channel of the rotary machine using a first force device removably coupled to a reaction bridge, the reaction bridge being coupled to the casing of the rotary machine, the reaction bridge including a first leg, a second leg, and a support beam extending therebetween, wherein the segment is repositioned within a portion of the arcuate channel; determining that the segment is mechanically frozen within the channel; and applying an outward force to the segment using a second force device removably coupled to the reaction bridge, wherein the segment is further repositioned within a portion of the arcuate channel.
 16. A method in accordance with claim 15, wherein applying the outward force to the segment further comprises coupling the second force device to the segment using a clevis assembly.
 17. A method in accordance with claim 16, wherein coupling the second force device to the segment further comprises: drilling a hole in an end of the segment end; and threadably coupling the second force device to the end of the segment.
 18. A method in accordance with claim 15, wherein applying an inward force to the segment further comprises applying the inward force substantially tangentially to the segment at a first end of the arcuate channel.
 19. A method in accordance with claim 18, wherein applying an outward force to the segment further comprises applying the outward force substantially tangentially to the segment at a second end of the arcuate channel.
 20. A method in accordance with claim 19 further comprising removing the segment from the second end of the arcuate channel. 